Airworthiness Directive · Amendment 39-18178 · Wings
Airbus Airplanes
This AD applies to the airplanes identified in paragraphs (c)(1) through (c)(5) of this AD, certificated in any category, all certified models, all serial numbers.
(1) Airbus Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and B4-203 airplanes.
(2) Airbus Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes.
(3) Airbus Model A300 B4-605R and B4-622R airplanes.
(4) Airbus Model A300 F4-605R and F4-622R airplanes.
(5) Airbus Model A300 C4-605R Variant F airplanes.
We are superseding Airworthiness Directive (AD) 2008-06-18 for all Airbus Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes); and Model A300 series airplanes. AD 2008- 06-18 required repetitive inspections for any cracking of the wing lower skin panel and associated internal support structure, and if necessary, corrective actions such as modifying the lower panel inboard of rib 9 aft of the rear spar and repairing cracks. This new AD continues to require actions required by AD 2008-06-18, and reduces certain compliance times. This AD was prompted by a report that information from an analysis and a fleet survey shows a need for reduced compliance times and intervals. We are issuing this AD to detect and correct cracking, which could lead to reduced structural integrity of the airplane.
This paragraph restates the requirements of paragraph (f) of AD 2008-06-18, Amendment 39-15430 (73 FR 14670, March 19, 2008), with revised service information. Unless already done, do the following actions.
(1) Except as provided by paragraphs (g)(1)(i), (g)(1)(ii), (g)(1)(iii), (g)(1)(iv), and (h) of this AD: At the threshold specified in paragraph 1.E.(2), “Accomplishment Timescale,” of Airbus Service Bulletin A300-57-0177, Revision 05, dated March 23, 2007 (for Model A300 series airplanes); Airbus Service Bulletin A300-57-6029, Revision 06, dated March 23, 2007 (for Model A300-600 series airplanes); or Airbus Service Bulletin A300-57-6029, Revision 08, dated April 25, 2013 (for Model A300-600 series airplanes); as applicable; perform the inspection of the wing lower skin panel and associated internal support structure aft of the rear spar and inboard of rib 9 and apply applicable corrective measures in accordance with Airbus Service Bulletin A300-57-0177, Revision 05, dated March 23, 2007 (for Model A300 series airplanes); Airbus Service Bulletin A300-57-6029, Revision 06, dated March 23, 2007 (for Model A300-600 series airplanes); or Airbus Service Bulletin A300-57-6029, Revision 08, dated April 25, 2013 (for Model A300-600 series airplanes); as applicable. All applicable corrective measures must be done at the applicable times specified in paragraph 1.E.(2) and the Accomplishment Instructions of Airbus Service Bulletin A300-57-0177, Revision 05, dated March 23, 2007 (for Model A300 series airplanes); Airbus Service Bulletin A300-57-6029, Revision 06, dated March 23, 2007 (for Model A300-600 series airplanes); or Airbus Service Bulletin A300-57-6029, Revision 08, dated April 25, 2013 (for Model A300-600 series airplanes); as applicable. Accomplishing the requirements of paragraph (h) of this AD terminates the requirements of this paragraph for Model A300-600 airplanes.
(i) Where the tables in paragraph 1.E.(2), “Accomplishment Timescale,” of Airbus Service Bulletin A300-57-0177, Revision 05, dated March 23, 2007; and Airbus Service Bulletin A300-57-6029, Revision 06, dated March 23, 2007; specify a grace period for doing the actions, this AD requires that the actions be done within the specified grace period relative to April 23, 2008 (the effective date of AD 2008-06-18, Amendment 39-15430 (73 FR 14670, March 19, 2008)).
(ii) Where the tables in paragraph 1.E.(2)(e), “Config 04,” of Airbus Service Bulletin A300-57-0177, Revision 05, dated March 23, 2007, specify an inspection interval but not an initial threshold, this AD requires that the actions be done within the specified interval after inspecting in accordance with Table 1A or 1B, as applicable, for Configuration 01 airplanes described in the Airbus Service Bulletin A300-57-0177, Revision 05, dated March 23, 2007, and thereafter at the inspection interval specified in the tables in paragraph 1.E.(2)(e), “Config 04,” of Airbus Service Bulletin A300-57-0177, Revision 05, dated March 23, 2007.
(iii) Where the tables in paragraph 1.E.(2)(f), “Config 05,” of Airbus Service Bulletin A300-57-6029, Revision 06, dated March 23, 2007, specify an inspection interval but not an initial threshold, this AD requires that the actions be done within the specified interval after inspecting in accordance with Table 1A, or 1B, as applicable, for Configuration 01 airplanes described in Airbus Service Bulletin A300-57-6029, Revision 06, dated March 23, 2007, and thereafter at the inspection interval specified in the tables in paragraph 1.E.(2)(f), “Config 05,” of Airbus Service Bulletin A300-57-6029, Revision 06, dated March 23, 2007.
(iv) All crack lengths specified in Airbus Service Bulletin A300-57-0177, Revision 05, dated March 23, 2007; and Airbus Service Bulletin A300-57-6029, Revision 06, dated March 23, 2007, are considered “not to exceed” lengths.
(2) Repeat the inspection at the intervals in, and according to the instructions defined in, Airbus Service Bulletin A300-57-0177, Revision 05, dated March 23, 2007 (for Model A300 series airplanes); Airbus Service Bulletin A300-57-6029, Revision 06, dated March 23, 2007 (for Model A300-600 series airplanes); or Airbus Service Bulletin A300-57-6029, Revision 08, dated April 25, 2013 (for Model A300-600 series airplanes); as applicable; except where Airbus Service Bulletin A300-57-0177, Revision 05, dated March 23, 2007, specifies repetitive inspections for cracking if Airbus Service Bulletin A300-57-022 has not been embodied, this AD requires doing repetitive inspections for cracking if Airbus Service Bulletin A300-57-0222 (modification 11178H5410) has not been embodied.
(3) Report to Airbus the first inspection results, whatever they may be, at the applicable time specified in paragraph (g)(3)(i) or (g)(3)(ii) of this AD.
(i) If the inspection was done after April 23, 2008 (the effective date of AD 2008-06-18, Amendment 39-15430 (73 FR 14670, March 19, 2008)), submit the report within 30 days after the inspection.
(ii) If the inspection was accomplished prior to April 23, 2008 (the effective date of AD 2008-06-18, Amendment 39-15430 (73 FR 14670, March 19, 2008)), submit the report within 30 days after April 23, 2008.
For Model A300-600 series airplanes, do the actions specified in paragraphs (h)(1) through (h)(3) of this AD at the applicable times specified in those paragraphs.
(1) Except as provided by paragraphs (h)(1)(i) and (h)(1)(ii) of this AD: Within the compliance times specified in Airbus Service Bulletin A300-57-6029, Revision 08, dated April 25, 2013, perform the inspection of the wing lower skin panels and associated internal support structures aft of the rear spar and inboard of rib 9, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6029, Revision 08, dated April 25, 2013. Thereafter, repeat these inspections at intervals specified in Airbus Service Bulletin A300-57-6029, Revision 08, dated April 25, 2013. Accomplishment of the actions required by this paragraph terminates the requirements of paragraph (g) of this AD for Model A300-600 airplanes.
(i) Where the tables in paragraph 1.E.(2), “Accomplishment Timescale,” of Airbus Service Bulletin A300-57-6029, Revision 08, dated April 25, 2013, specify a grace period for doing the actions for airplanes that have exceeded the thresholds, this AD requires, for all airplanes, that the actions be done within the specified grace period after the effective date of this AD or before the specified thresholds, whichever occurs later.
(ii) Where Airbus Service Bulletin A300-57-6029, Revision 08, dated April 25, 2013, specifies to “contact Airbus” before further flight, this AD requires repairing using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA); and accomplishing those actions before further flight. If approved by the DOA, the approval must include the DOA-authorized signature.
(2) If, during any inspection as required by paragraph (h)(1) of this AD, discrepancies are detected, before next flight, accomplish the applicable corrective actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6029, Revision 08, dated April 25, 2013.
(3) Corrective actions, as required by paragraph (h)(2) of this AD, do not constitute terminating action for the repetitive inspection requirements of paragraph (h)(1) of this AD.
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
